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IEEE Transactions on Aerospace and Navigational Electronics

Issue 0 • Date Oct. 1963

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Displaying Results 1 - 25 of 64
  • Tenth Annual East Coast Conference on Aerospace and Navigational Electronics

    Publication Year: 1963, Page(s): c1
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  • Technical Papers

    Publication Year: 1963, Page(s):i - ii
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  • Chairman's Message

    Publication Year: 1963, Page(s): iii
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  • [Table of contents]

    Publication Year: 1963, Page(s):iv - ix
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  • Introduction

    Publication Year: 1963, Page(s): xi
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  • Radiation Effects - I

    Publication Year: 1963, Page(s): 1.1-1
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  • Space Vehicle Attitude Control

    Publication Year: 1963, Page(s): 1.2-1
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  • A Planetary Orbiting Relay Communication Link for Project Voyager

    Publication Year: 1963, Page(s):1.3.1-1 - 1.3.1-8
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1007 KB)

    Beginning in the late 1960's Voyager spacecraft will be launched to Venus and Mars. These spacecraft may contain both orbiting and landing modules. One of the first questions which arises in such a system is whether to transmit the data originating in the lander directly back to earth or to relay through the orbiter. This paper discusses the theoretical, operational and environmental aspects of th... View full abstract»

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  • Electronic Solar Flare Alarm System

    Publication Year: 1963, Page(s):1.3.2.1 - 1.3.2.15
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (4319 KB)

    This paper describes the work done in designing and breadboarding a solar flare alarm system employing video digital techniques. The conceptual design of the system is presented, and experimental apparatus, solar and flare simulation equipment, and procedures employed in obtaining performance data are described. Experimental measurements and results are included. In general, it was found that the ... View full abstract»

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  • Electrical Solar Power Supply Systemi Considerations for UK-2/S-52 International Satellite

    Publication Year: 1963, Page(s):1.3.3-1 - 1.3.3-3
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (572 KB)

    The UK-2/S-52 Satellite is one of NASA's International Satellites and carries Experiments built by the British. The satellite is under Management and technical supervision of Goddard Space Flight Center. The Consideration and analysis of environmental and operational requirements, as well as the requirements imposed by the satellite configuration, influenced the UK-2/S-52 power source system desig... View full abstract»

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  • Radar System Design for Spacecraft Terminal Control

    Publication Year: 1963, Page(s): 1.3.4-1
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (64 KB)

    This paper discusses the design of radar for use in the terminal control of manned and umanned space vehicles of the maneuverable type. In order to present the requirements and specifications of the required radar, the type of missions that will use terminal control are discussed. Also terminal control equipment suchl as analogue computers and displays are mentioned in preserting these specificati... View full abstract»

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  • The UK-2/S-52 International Satellite

    Publication Year: 1963, Page(s):1.3.5-1 - 1.3.5-3
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1253 KB)

    The S-52 (See Figure 1) is being built under the cooperative international program being conducted by the United States and the United Kingdom. In the U.K., University and Government, Laboratories designed and constructed the instrumentation for the S-52 experiments under the scientific direction of the British National Committee for Space Research. The Goddard Space Flight Center, for NASA, has o... View full abstract»

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  • Microelectronic Devices for Application in Transient Nuclear Radiation Environments

    Publication Year: 1963, Page(s):1.4.1-1 - 1.4.1-6
    Cited by:  Papers (2)
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (984 KB)

    The results of environmental tests designed to determine the relative susceptibility of monolithic silicon and thin fillm integrated circuits and devices to the transient nuclear radiation environment associated with a nuclear explosion are discussed. These results strorngly indicate that hybrid thin film circuits employing high frequency transistors should be used in systems now being designed wh... View full abstract»

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  • Test Techniques for Transient Radiation Effects

    Publication Year: 1963, Page(s):1.4.2.1 - 1.4.2.12
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1295 KB)

    This paper gives examples of specific test techniques which have been used in performing transient radiation effects test measurements. The techniques were developed primarily for use with electron linear accelerators but can be applied directly in flash X-ray and pulsed reactor test programs as well. View full abstract»

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  • An Estimate of Radiation Effects on Electronic Compoents for the Lunar Excursion Module

    Publication Year: 1963, Page(s):1.4.3-1 - 1.4.3-11
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1464 KB)

    The various radiation sources (solar flares and natural and artificial Van Allen Belts) to be encountered on the Apollo Mission have been compared with regard to effect on electronic components. It is found that a large Class 3+ flare constitutes the most serious hazard. We have assumed that such a flare will occur and have calculated the degradation in performance of electronic components caused ... View full abstract»

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  • Selection of Radiation Qualified Semiconductor Electronics for Space System Design

    Publication Year: 1963, Page(s):1.4.4-1 - 1.4.4-7
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    Factors controlling the evaluation of radiation vulnerability of transistors, diodes, and solar cells are reviewed. Typical results from computer analysis of transistor current gain degradation are presented, emphasizing dependence of degradation on dc operating point. Particle equivalence for permanent radiation damage in semiconductor devices is summarized. Extention of operational lifetime of s... View full abstract»

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  • A Nuclear Radiation Resistant Control Moment Gyroscope

    Publication Year: 1963, Page(s):1.4.5-1 - 1.4.5-8
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1498 KB)

    The nuclear radiation resistant control moment gyroscope is a sensing and control device intended for service in space vehicles with nuclear radiation environment. Its main function is to control the altitude and stability of a spacecraft in orbit. The nuclear radiation resistance is achieved through the highly selective use of radiation resistant materials in the design. One such gyro has been gr... View full abstract»

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  • Digital Attitude Control System for Spacecraft

    Publication Year: 1963, Page(s):1.5.1-1 - 1.5.1-10
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (2165 KB)

    For attitude control of certain classes of spacecraft, digital techniques appear to offer distinct advantages over analog systems. A program was conducted to evaluate experimentally a stabilization and control system in which digital methods are used for measurement, signal processing, and torque control. The logic design of the control system is discussed in detail, and the hardware used for impl... View full abstract»

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  • Fine Pointing Control for the Orbiting Astronomical Observatory (Oao)

    Publication Year: 1963, Page(s):1.5.2-1 - 1.5.2-5
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (800 KB)

    High pointing accuracy requirements are imposed on the control system of the OAO. One tenth arcsec angular accuracy can be achieved in orbiting spacecraft using star references, long focal length optical systems, and relatively small torquing devices. Noise problems are introduced when a single error sensor is required to track stars with greatly different magnitudes. As star magnitude decreases, ... View full abstract»

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  • An Attitude Control System for the Advanced Orbiting Solar Observatory

    Publication Year: 1963, Page(s):1.5.3-1 - 1.5.3-3
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  • Fine Sun Tracker for Advanced Orbiting Solar Observatory

    Publication Year: 1963, Page(s):1.5.4-1 - 1.5.4-10
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1555 KB)

    The analysis and design of a fine sun tracker for the Advanced Orbiting Solar Observatory are discussed. The tracker provides accurate pointing information in pitch and yaw, permitting precise static and dynamic orientation of the observatory with respect to the sun's apparent disc, in accordance with ground commands. The tracker uses a servo driven optical slab in each axis to offset the optical ... View full abstract»

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  • A Stability Criterion for an Artificial Earth Satellite

    Publication Year: 1963, Page(s):1.5.5-1 - 1.5.5-10
    Cited by:  Papers (1)
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1247 KB)

    The equation of rotation of the spacecraft about a set of control axes are developed to reveal the required functions of a momentum exchange control system when subjected to external disturbances. A linear control system is designed and the three-axis characteristic equation is developed. This ninth order equation has coefficients which vary with the particular attitude references in use, and with... View full abstract»

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  • Piloted Flight Simulation

    Publication Year: 1963, Page(s): 1.6.1
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  • Space Eivironment

    Publication Year: 1963, Page(s):2.1.1 - 2.1.2
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  • Gemini Range and Range Rate Measuring System

    Publication Year: 1963, Page(s):2.2.1-1 - 2.2.1-8
    Request permission for commercial reuse | Click to expandAbstract | PDF file iconPDF (1621 KB)

    To complete the terminal phase of a space rendezvous mission, it is essential that accurate indications of target vehicle range and relative range rate be presented to the astronauts commanding the chaser vehicle. The indicator characteristics and the method of data presentation assume prime importance in compliance with the above. Therefore, a discussion is given of the logical development and fu... View full abstract»

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Aims & Scope

This Transactions ceased publication in 1965. The new retitled publication is IEEE Transactions on Aerospace and Electronic Systems.

Full Aims & Scope